CN117227966A - Automatic calibration method for zero position of control surface of airplane flap - Google Patents
Automatic calibration method for zero position of control surface of airplane flap Download PDFInfo
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Abstract
The application provides an automatic calibration method for the position zero position of a flap control surface of an airplane, which belongs to the technical field of high lift of the airplane, and particularly comprises that two flap control computers of the airplane both store flap electric position data when the flap control surface is adjusted to a mechanical zero position, and the flap control computers send the flap electric position data in the flap position data with a data use mark in an invalid state to a rear-end crosslinked flap power driving controller as flap zero position data; when one of the flap control computers is replaced, the central maintenance system obtains new flap position zero position data according to the flap electric position data of the two flap control computers and the flap electric position data of the two flap power driving controllers. By the processing scheme, the zero calibration efficiency and reliability of the replacement flap position of the external field spare part are improved, maintenance work is simplified, and potential safety hazards are eliminated.
Description
Technical Field
The application relates to the field of high lift of aircraft, in particular to an automatic zero position calibration method for the control surface position of an aircraft flap.
Background
Modern large-scale aircraft are equipped with high lift systems, and the wing surface area is increased by controlling the outward extension of the front part and the slat in low-speed states such as take-off and landing of the aircraft, and the wing profile is changed by downwards bending to improve the lift of the aircraft, so that the reasonable running distance and the safe take-off speed of the aircraft are ensured, and meanwhile, the climbing rate, the approach speed and the approach flight attitude of the aircraft are improved. The flap control computer is a core component of the high lift system. Each aircraft is typically configured with two identical flap control computers, each configured with a command channel and a monitor channel. The flap control computer commands and the monitoring channels respectively acquire the information of the control handle and the airfoil position sensor, and position closed-loop control is carried out after control law calculation. Therefore, the mechanical zero position of the wing flap airfoil and the accuracy of the electric zero position of the wing flap position acquired by the wing flap control computer have great influence on the control accuracy of the whole high lift system, and the inaccurate mechanical zero position and electric zero position can also cause asymmetrical false alarm faults of the wing flap airfoil to influence the flight safety. When the flap control computer is replaced, personnel are required to adjust the position of the flap airfoil, and then the electric zero position of the flap position is collected again, so that the efficiency is low, and the requirement on maintenance environment is high.
The current stage treatment mode comprises the following steps: when the aircraft enters the final assembly stage, aircraft assembly personnel install the left flap airfoil and the right flap airfoil and perform mechanical zeroing operation so as to ensure that the airfoil installation position meets the design requirement. However, since the above-mentioned work is generally done manually, it is practically unavoidable that there is an error in the mounting positions of the left and right airfoils and the design requirements and an error in the positions between the left and right airfoils. In order to solve the serious problems that the information of the flap position acquisition is inaccurate and even the wing surface is asymmetric possibly caused by mechanical zeroing errors, the electric zero position acquisition work still needs to be carried out when the flap control computer is initially installed on the aircraft. The specific process is as follows: after confirming that the mechanical position of the airfoil surface basically meets the mechanical zero design requirement, the flap control computer enters a ground maintenance mode, the command and monitoring channels respectively read the information of the flap position sensors crosslinked by the channels, if the read flap position information meets the system allocation index, the data are valid, the data are stored in a nonvolatile memory (NVRAM) of the computer to be used as the electric zero position of the flap position operated by software, and if the acquired data exceeds the system allocation index, the mechanical zero setting and electric zero position acquisition work is carried out again until the requirements are met.
Although the processing mode can effectively avoid the problems of possible control precision, asymmetrical flaps and the like caused by mechanical zero position installation position errors of the flap airfoil, each operation depends on adjustment of mechanical zero position and matching of ground maintenance equipment, and under specific conditions, particularly under tension conditions, the aircraft needs to quickly replace spare parts and calibration of the zero position of the flap airfoil cannot be carried out under the conditions of lack of maintenance equipment in an external field. In this case, if mechanical zeroing is required and the flap position is adjusted by the flap control computer using the outfield ground maintenance device, the replacement spare part is put into service at a time, which obviously cannot meet the actual combat requirements.
Disclosure of Invention
In view of the above, the application provides an automatic calibration method for the position zero position of the control surface of the flap of the airplane, which solves the problems in the prior art, improves the calibration efficiency and reliability of the position zero position of the replacement flap of the spare part of the external field, simplifies maintenance work and eliminates potential safety hazards.
The application provides an automatic calibration method for the position zero position of a control surface of an airplane flap, which adopts the following technical scheme:
an automatic calibration method for the zero position of a control surface of an airplane flap comprises the following steps:
step 1, two flap control computers of an airplane both store flap electric position data when flap control surfaces are adjusted to mechanical zero positions, the flap electric position data comprise flap electric position data and whether the data use marks or not, and whether the initial state of the data use marks is set to be invalid or not;
step 2, the flap control computer sends the flap electric position data in the flap position data with the invalid state of the data use flag to the rear-end crosslinked flap power driving controller as flap zero position data, and the rear-end crosslinked flap power driving controller stores the received flap electric position data, and the flap control computer changes the valid state of the data use flag and stores the valid state of the data use flag to the flap control computer;
step 3, when only one flap control computer is replaced, the two flap control computers respectively send flap electric position data to a central maintenance system of the aircraft as first data and second data, the two flap power driving controllers send the flap electric position data to the central maintenance system of the aircraft as third data and fourth data, the central maintenance system makes a difference value between the first data and the third data, the first data and the fourth data makes a difference value between the second data and the third data, and the second data and the fourth data do a difference value;
when the four difference values are smaller than the threshold value, taking the average value of the first data, the second data, the third data and the fourth data as new flap position zero position data;
when the difference value between the first data and the third data is smaller than the threshold value, the difference value between the first data and the fourth data is smaller than the threshold value, and the difference value between the first data and the second data is larger than the threshold value, taking the average value of the first data, the third data and the fourth data as new flap position zero position data;
when the difference value between the second data and the third data is smaller than the threshold value, the difference value between the second data and the fourth data is smaller than the threshold value, and the difference value between the first data and the second data is larger than the threshold value, taking the average value of the second data, the third data and the fourth data as new flap position zero position data;
and sending the new flap position zero data to the two flap control computers and the two flap power driving controllers.
Optionally, in step 3, when the difference between the first data and the third data is greater than the threshold, the difference between the first data and the fourth data is greater than the threshold, and the difference between the first data and the second data is greater than the threshold, repeating step 1 and step 2 to obtain the flap electric position data when the flap control surface is adjusted to the mechanical zero position again;
the difference value between the first data and the third data is larger than a threshold value, the difference value between the first data and the fourth data is larger than the threshold value, the difference value between the first data and the second data is smaller than the threshold value, and the step 1 and the step 2 are repeated to acquire the electric position data of the flap when the control surface of the flap is regulated to the mechanical zero position again;
the difference value between the first data and the third data is smaller than a threshold value, the difference value between the first data and the fourth data is larger than the threshold value, and the step 1 and the step 2 are repeated to acquire the flap electric position data when the flap control surface is regulated to the mechanical zero position again;
the difference value between the second data and the third data is larger than a threshold value, the difference value between the second data and the fourth data is larger than a threshold value, the difference value between the first data and the second data is larger than a threshold value, and the step 1 and the step 2 are repeated to acquire the electric position data of the flap when the control surface of the flap is regulated to the mechanical zero position again;
and (3) the difference value between the second data and the third data is larger than a threshold value, the difference value between the second data and the fourth data is larger than the threshold value, the difference value between the first data and the second data is smaller than the threshold value, and the step (1) and the step (2) are repeated to acquire the electric position data of the flap when the control surface of the flap is regulated to the mechanical zero position again.
Optionally, in step 1, when the aircraft is in an initial state, the flap control surfaces of the aircraft are adjusted to a mechanical zero position, the two flap control computers collect flap electrical position data when the flap control surfaces are adjusted to the mechanical zero position, and the data of the flap electrical position data when the flap control surfaces are adjusted to the mechanical zero position are stored in the two flap control computers.
Optionally, the data of the flap electrical position data when the flap control surface is adjusted to the mechanical zero position is stored on NVRAM of both flap control computers.
Optionally, in step 2, before the flap control computer sends the flap electric position data in the flap position data marked as invalid as the flap zero position data to the back-end crosslinking flap power driving controller, the method further includes: the two flap control computers respectively judge whether the respective flap control computer is in normal communication with the flap power driving controller of the rear-end crosslinking equipment, and if so, judge whether the data of the flap position data use the state of the mark.
Optionally, in step 3, after sending the new flap position zero data to the two flap control computers and the two flap power driving controllers, the method further includes: the two flap control computers and the two flap power drive controllers store the received new flap position zero data.
In summary, the application has the following beneficial technical effects:
the method covers the zeroing of the flap position and the realization process, and the function description is complete;
the method does not need additional hardware resource support, and has the characteristics of low implementation cost and strong usability;
the method can realize quick zeroing of the flap control surface, and has high efficiency and reliability.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic flow diagram of a stage of acquisition of the electrical zero position of the flap position of the present application;
FIG. 2 is a flow chart of the application program operation stage of the present application.
Detailed Description
Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present application with reference to specific examples. It will be apparent that the described embodiments are only some, but not all, embodiments of the application. The application may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present disclosure, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concept of the present application by way of illustration, and only the components related to the present application are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
The embodiment of the application provides an automatic calibration method for the zero position of a control surface of an airplane flap.
An automatic calibration method for the zero position of a control surface of an airplane flap is characterized by comprising the following steps:
step 1, two flap control computers of an airplane both store flap electric position data when flap control surfaces are adjusted to mechanical zero positions, the flap electric position data comprise flap electric position data, whether the data use marks or not, and whether the initial state of the data use marks is set to be invalid or not.
And 2, the flap control computer sends the flap electric position data in the flap position data with the invalid state of the data use flag to the rear-end cross-linked flap power driving controller as flap zero position data, and the rear-end cross-linked flap power driving controller stores the received flap electric position data, and the flap control computer changes the valid state of the data use flag and stores the valid state of the data use flag to the flap control computer.
Step 3, when only one flap control computer is replaced, the two flap control computers respectively send flap electric position data to a central maintenance system of the aircraft as first data and second data, the two flap power driving controllers send the flap electric position data to the central maintenance system of the aircraft as third data and fourth data, the central maintenance system makes a difference value between the first data and the third data, the first data and the fourth data makes a difference value between the second data and the third data, and the second data and the fourth data do a difference value;
when the four difference values are smaller than the threshold value, taking the average value of the first data, the second data, the third data and the fourth data as new flap position zero position data;
when the difference value between the first data and the third data is smaller than the threshold value, the difference value between the first data and the fourth data is smaller than the threshold value, and the difference value between the first data and the second data is larger than the threshold value, taking the average value of the first data, the third data and the fourth data as new flap position zero position data;
when the difference value between the second data and the third data is smaller than the threshold value, the difference value between the second data and the fourth data is smaller than the threshold value, and the difference value between the first data and the second data is larger than the threshold value, taking the average value of the second data, the third data and the fourth data as new flap position zero position data;
and sending the new flap position zero data to the two flap control computers and the two flap power driving controllers.
In the step 3, when the difference value between the first data and the third data is larger than a threshold value, the difference value between the first data and the fourth data is larger than a threshold value, and the difference value between the first data and the second data is larger than a threshold value, repeating the step 1 and the step 2 to acquire the electric position data of the flap when the control surface of the flap is regulated to the mechanical zero position again;
the difference value between the first data and the third data is larger than a threshold value, the difference value between the first data and the fourth data is larger than the threshold value, the difference value between the first data and the second data is smaller than the threshold value, and the step 1 and the step 2 are repeated to acquire the electric position data of the flap when the control surface of the flap is regulated to the mechanical zero position again;
the difference value between the first data and the third data is smaller than a threshold value, the difference value between the first data and the fourth data is larger than the threshold value, and the step 1 and the step 2 are repeated to acquire the flap electric position data when the flap control surface is regulated to the mechanical zero position again;
the difference value between the second data and the third data is larger than a threshold value, the difference value between the second data and the fourth data is larger than a threshold value, the difference value between the first data and the second data is larger than a threshold value, and the step 1 and the step 2 are repeated to acquire the electric position data of the flap when the control surface of the flap is regulated to the mechanical zero position again;
and (3) the difference value between the second data and the third data is larger than a threshold value, the difference value between the second data and the fourth data is larger than the threshold value, the difference value between the first data and the second data is smaller than the threshold value, and the step (1) and the step (2) are repeated to acquire the electric position data of the flap when the control surface of the flap is regulated to the mechanical zero position again.
The data of the flap electric position data when the flap control surface is adjusted to the mechanical zero position are stored on NVRAM of the two flap control computers.
In one embodiment:
as shown in fig. 1, the flap position electrical zero acquisition phase: and adjusting the flap control surface to a mechanical zero position, and adjusting to meet the required precision requirement. The flap system is set in a maintenance mode, the two flap control computers respectively collect the flap position electrical zero data and store the flap position electrical zero data into NVMs of the channels, and the stored data comprise flap position collection values, data valid marks and data use marks. The data valid flag is determined according to whether actually collected flap position data meets the designed margin requirement and whether the checksum is correct, and whether the data use flag is set to be invalid.
As shown in fig. 2, the application program run phase. The flap control computer software initialization phase reads the flap position data stored in the NVRAM and judges the validity of the data. And if the data are valid, the flap position data stored in the NVRAM are used as flap position zero position values used by software operation, otherwise, default flap position zero position data are used. The two flap control computers respectively judge whether the respective flap control computer is in normal communication with the flap power driving controller crosslinked at the rear end. If the communication is normal and the data valid flag is valid, and whether the data use flag is in an invalid state, the flap control computer sends the flap position zero data stored in the NVRAM to the rear-end flap power drive controller, and meanwhile, the flap control computer changes whether the data use flag is in a valid state and stores the updated data into the NVRAM. If the above conditions are not met, the flap control computer does not send flap position zero data to the trailing flap power drive controller.
In step 3, after sending the new flap position zero data to the two flap control computers and the two flap power drive controllers, the method further comprises: the two flap control computers and the two flap power drive controllers store the received new flap position zero data.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the application is subject to the protection scope of the claims.
Claims (6)
1. An automatic calibration method for the zero position of a control surface of an airplane flap is characterized by comprising the following steps:
step 1, two flap control computers of an airplane both store flap electric position data when flap control surfaces are adjusted to mechanical zero positions, the flap electric position data comprise flap electric position data and whether the data use marks or not, and whether the initial state of the data use marks is set to be invalid or not;
step 2, the flap control computer sends the flap electric position data in the flap position data with the invalid state of the data use flag to the rear-end crosslinked flap power driving controller as flap zero position data, and the rear-end crosslinked flap power driving controller stores the received flap electric position data, and the flap control computer changes the valid state of the data use flag and stores the valid state of the data use flag to the flap control computer;
step 3, when only one flap control computer is replaced, the two flap control computers respectively send flap electric position data to a central maintenance system of the aircraft as first data and second data, the two flap power driving controllers send the flap electric position data to the central maintenance system of the aircraft as third data and fourth data, the central maintenance system makes a difference value between the first data and the third data, the first data and the fourth data makes a difference value between the second data and the third data, and the second data and the fourth data do a difference value;
when the four difference values are smaller than the threshold value, taking the average value of the first data, the second data, the third data and the fourth data as new flap position zero position data;
when the difference value between the first data and the third data is smaller than the threshold value, the difference value between the first data and the fourth data is smaller than the threshold value, and the difference value between the first data and the second data is larger than the threshold value, taking the average value of the first data, the third data and the fourth data as new flap position zero position data;
when the difference value between the second data and the third data is smaller than the threshold value, the difference value between the second data and the fourth data is smaller than the threshold value, and the difference value between the first data and the second data is larger than the threshold value, taking the average value of the second data, the third data and the fourth data as new flap position zero position data;
and sending the new flap position zero data to the two flap control computers and the two flap power driving controllers.
2. The automatic calibration method for the position zero position of the control surface of the flap of the aircraft according to claim 1, wherein in the step 3, when the difference between the first data and the third data is larger than a threshold value, the difference between the first data and the fourth data is larger than the threshold value, the difference between the first data and the second data is larger than the threshold value, the step 1 and the step 2 are repeated to acquire the electric position data of the flap when the control surface of the flap is adjusted to the mechanical zero position again;
the difference value between the first data and the third data is larger than a threshold value, the difference value between the first data and the fourth data is larger than the threshold value, the difference value between the first data and the second data is smaller than the threshold value, and the step 1 and the step 2 are repeated to acquire the electric position data of the flap when the control surface of the flap is regulated to the mechanical zero position again;
the difference value between the first data and the third data is smaller than a threshold value, the difference value between the first data and the fourth data is larger than the threshold value, and the step 1 and the step 2 are repeated to acquire the flap electric position data when the flap control surface is regulated to the mechanical zero position again;
the difference value between the second data and the third data is larger than a threshold value, the difference value between the second data and the fourth data is larger than a threshold value, the difference value between the first data and the second data is larger than a threshold value, and the step 1 and the step 2 are repeated to acquire the electric position data of the flap when the control surface of the flap is regulated to the mechanical zero position again;
and (3) the difference value between the second data and the third data is larger than a threshold value, the difference value between the second data and the fourth data is larger than the threshold value, the difference value between the first data and the second data is smaller than the threshold value, and the step (1) and the step (2) are repeated to acquire the electric position data of the flap when the control surface of the flap is regulated to the mechanical zero position again.
3. The method for automatically calibrating the position zero position of the control surface of the flap of the airplane according to claim 1, wherein in the step 1, when the airplane is in an initial state, the control surface of the flap of the airplane is adjusted to a mechanical zero position, the two flap control computers collect flap electric position data when the control surface of the flap is adjusted to the mechanical zero position, and the data of the flap electric position data when the control surface of the flap is adjusted to the mechanical zero position are stored in the two flap control computers.
4. The method for automatic calibration of the position zero position of the control surface of a flap of an aircraft according to claim 1, characterized in that the data of the electric position data of the flap when the control surface of the flap is adjusted to the mechanical zero position are stored on NVRAM of two flap control computers.
5. The method for automatically calibrating the position zero position of the control surface of the flap of the aircraft according to claim 1, wherein in the step 2, before the flap control computer sends the flap electric position data in the flap position data with the invalid state as the flap zero position data to the rear-end cross-linked flap power driving controller, the method further comprises: the two flap control computers respectively judge whether the respective flap control computer is in normal communication with the flap power driving controller of the rear-end crosslinking equipment, and if so, judge whether the data of the flap position data use the state of the mark.
6. The method for automatically calibrating the position zero position of the control surface of the flap of the airplane according to claim 1, wherein in the step 3, after sending the new flap position zero position data to the two flap control computers and the two flap power driving controllers, the method further comprises: the two flap control computers and the two flap power drive controllers store the received new flap position zero data.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311062020.7A CN117227966A (en) | 2023-08-22 | 2023-08-22 | Automatic calibration method for zero position of control surface of airplane flap |
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| CN202311062020.7A CN117227966A (en) | 2023-08-22 | 2023-08-22 | Automatic calibration method for zero position of control surface of airplane flap |
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